Gyroscopic and aerodynamic stabilizer



July 8, 1930. N.CLARK GYROSCOPIC AND AERODYNAMIC STABILIZER Filed July 3, 1929 2 Sheets-Sheet l gwvewl 01/ Norman war/13 July 8, 1930. N. CLARK GYROSCOPIC AND AERODYNAMIC STABILIZER' Filed July 3, 1929 2 Sheets-Sheet 2 Patented July 1930 a "Roman CLARK, or CANTON, OHIO 4 GYROSCOPIC AND AERODYNAMIC STABILIZER I Application filed July 3, 1929. Serial No. 375,704.

My invention relates to stabilizers for use more particularly with airplanes for increasing their inherent stability and lift.

It is well known that the usual airplane is 5 given a certain degree of inherent stability by the use of a lateral dihedral angle between the main planes and a longitudinal dihedral angle between the center section of the main planes and the stationary portions of the elevator surfaces of the tail.

The operation of such stabilizing means depends on a slight displacement of the airplane towards an unstable position in which position a balancing aerodynamicv force is brought into play. v

In other words, the usual stabilizing means are arerodynamic in nature, and thus require the presence of air and atime element-for their operation.

Under certain conditions, as-for example,

when the right wing of an airplane suddenly runs into an air pocket, that is to say a region of less pressure than that surrounding the left wing, the difference in pressure betweenthe air surrounding the right and left wings may be of such magnitude as to preventthe automatic operation of the aerodynamic stabilizing means provided'by the usual lat eral dihedral angle between the right and left wings.

In such a case, if the pilot is not successful in his manipulations ofthe wing flaps or ailerons, the plane will roll, and may maneuver entirely out of the ilots control. I

The objects of't e present improvements include the provision of stabilizing means, which are-not entirely of aerodynamic charactor, and which include mechanical means which may be constantly operated to main- 40 tain the plane in the proper positionffor normal horizontal flight.

Further objects of the improvements include the provision of stabilizing means which are partly aerodynamic ,in character, and 4 which include aerodynamic means for increasing the lift on the airplane, independently of the lift arising from the reactions of the main wing surfaces.

Further ob ects of the improvements in clude the provision of novel means for controlling and varying the operation of the niechanical and aerodynamic elements of theimproved stabilizer.

These objects are attained by the improved stabilizer comprising the presentinvention, which may be described in general terms as including a combined gyroscope and helicopter whose axis of rotation is arranged with respect to the other airplane parts, so that the gyroscopic actionof the stabilizer will maintain the airplane in the required position for normal horizontal flight, and the lifting power of the helicopter will increase the lift of the airplane, particularly at the lower flying. speeds, and the gyroscope and helicopter means being relatively variable in'operation.

A preferred embodiment of the invention is illustrated in the accompanying drawings forming part hereof, in which -Figure 1 is a plan elevation of an airplane equipped with a preferred'embodiment of the improved stabilizer hereof Fig. 2, a frontelevation' thereof;

Fig. 3, a side elevation thereof;

Fig. 4, an enlarged fragmentary plan view thereof Fig. 5, an axial sectional view thereof as on line 55, Fig. 4, the helicopter blade being illustrated in operative position; Fig. 6, a fragmentary sectional view of the improved stabilizer .as on line 6 6, Fig. 5; Fig. a fragmentary sectional view thereof as on line 7-7, Fig. 6; and Fig. 8, a fragmentary sectional view thereof as on line 88, Fig. 5 illustrating one form of control means forthe apparatus.

Similar numerals refer to similar parts throughout the several views. The improved stabilizer of the present invention indicated generally at 10 may be applied to' any type of aircraft, but is here illustrated in use on a monoplate' indicated gen erally at 11. I

The improved stabilizer'lO includes a gyroscope wheel 12 preferably including a lower cone 13 having a wide apex angle, and having its apex below its base, and the base terminating in an annular flange 14 of considerable mass for increasing the gyfoscopic efiect of. i

the stabilizer.

An upper cone also having a wide apex angle preferably equal to the apex angle of the cone 13, and having its apex above its base, is seated at its base in an annular socket 16 formed in the base of the lower cone, and the cones are secured to each other at their bases as by screws 17. p

The cones 13 and 15 may have their masses decreased between their central hub portions and the annular" flange 18 and 19, respectively,

with internal. hollow 14, by forming them conical chambers 20 and 21, respectively.

The lower cone includes radially extending angle walls 22 and 23- nfierging..with.,walls 24 and'25 in' the upper cone for forming of a drive shaft 30.

The drive shaft extends throughthe center of gravity of the airplane, from a gear connection 31 with an extension 32 of the aircraft engine drive shaft, upwardly through bearings 33 carried in a suitable mounting bracket of the airplane wing 35, and the gyroscope and helicopter wheel are secured as aforesaid on the upper end of the shaft 30.

The shaft 30 is located in thelongitudinal plane of symmetry of the airplane, and its angular relation with the longitudinal axis of the airplane is fixed so that when the plane of rotation of the wheel12 is horizontal, the airplane is in the position for normal horizontal flight, r I I Thus when :the wheel 12 is rotated, the

\ gyroscopic effect of the wheel will resist any deviatingmovement about a horizontal axis .of the aircraft from the position for normal horizontal flight.

. When the helicopter slot cover blades 27 are in the elevated position illustrated in Figs. 5 and 6, and the rotation of the wheel being counter clockwise as illustrated in Fig. 4, th blades and the slots willhave a helicopter action when rotating through the air,

and will provide additional lift for the air-' plane. i I

Means are provided for adjusting the positions of the helicopter blade during rotation of the wheel, and such means may include a lug 36 depending from the lower surface of each blade 27, and each lug is pivotally connected with one end of an operating link37 extending downwardly through the slot for the particular blade.

The lower end of each link 37 is pivotally connected with a sleeve 38 slidably keyed on the shaft 30, and the sleeve 38 has rotatably 34 secured .upon the top mounted thereon a collar 39 which is maintained stationary with respect to rotation, and may be carried at the upper ends of rods 40 and 40' which are mounted for vertically sliding in the bracket 34 The lower ends of the rods 40 and 40 are provided with a slot and pivot connection with the outer end of an operating crank 41 mounted on a pivot 42 within the airplane fuselage, and connected with a handle lever 43 which is preferably provided with ratchet ,means indicated generally at 44 for maintaining the handle lever and operating crank 41 in any desired position of adjustment.

Thus by rotary'm'ovement of the handle lever 43 about the pivot 42, the operating crank 41 will raiseand lower the rodsv 40 and 40, and will thus raise and lower the sleeve 38 and the blades 27 through the links 37, thereby permitting any degree of opening for the helicopter blades 27, and permitting any desired amount of air to be diverted downwardly through the slots 26.

. I claim:

1. A stabilizer for aircraft and the like including a gyroscope wheel comprising top and bottom conical walls having their bases abuttin in the central plane of the wheel, and wa ls of the wheel forming angledradially extending helicopter slots.

2. A stabilizer for aircraft and the like including a gyroscopewheel comprising top and bottom conical walls having their bases abutting in the central plane of the wheel,

and walls of thewheel forming angled radiallyextending helicopter slots, and an adjustable closure member for eachslot.

3. A' stabilizer for aircraft and the like, including a gyroscope wheel comprising top and bottom conical walls having, their basesabuttin in the central, plane of the wheel, walls 0% the wheel forming angled radially extending helicopter slots, and a helicopter bllade mounted upon the wheel adjacent each s ot.

4. A'stabilizer for aircraft and .the like, including a gyroscope wheel, comprising'top and bottom conical walls having their bases abutting inthe central plane of the wheel, walls of the wheel forming angled radially extending helicopter slots, and a helicopter blade hinged upon'the wheel adjacent each slot and adapted to. close the slot. -5. A stabilizer for aircraft and the like, including a gyroscope wheel comprising top and bottom conical walls having their bases abutting in the central plane of the wheel, walls of the wheel forming angled radially extending helicopter slots, and a helicopter blade-hinged upon the wheel adjacent each slot, and means for manipulating the blades for opening. and closing the respective slots. In testimony that I claim the above, I have hereunto subscribed my name.

. NORMAN CLARK. 

